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Description
  • This paper presents the ongoing first steps of development of an innovative centrifugal compressor stage designed for use in turboprop aircraft engines. The so-called tandem impeller blading concept shall be compared to the conventional blading design by means of numerical simulation and optimized to achieve the best possible parameters. In this paper, validation of a conventional stage computational model using experimental data is described.
  • This paper presents the ongoing first steps of development of an innovative centrifugal compressor stage designed for use in turboprop aircraft engines. The so-called tandem impeller blading concept shall be compared to the conventional blading design by means of numerical simulation and optimized to achieve the best possible parameters. In this paper, validation of a conventional stage computational model using experimental data is described. (en)
Title
  • A Computational Model of a Centrifugal Compressor Stage for Aircraft Engines
  • A Computational Model of a Centrifugal Compressor Stage for Aircraft Engines (en)
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  • A Computational Model of a Centrifugal Compressor Stage for Aircraft Engines
  • A Computational Model of a Centrifugal Compressor Stage for Aircraft Engines (en)
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  • RIV/68407700:21220/14:00221397!RIV15-MSM-21220___
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  • S
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  • 647
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  • RIV/68407700:21220/14:00221397
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  • centrifugal compressor; turboprop engine; impeller; vaned diffuser; secondary flow; CFD (en)
http://linked.open.../riv/klicoveSlovo
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  • [DC662F7DDFEC]
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  • Praha
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  • Praha
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  • Studentská tvůrčí činnost 2014
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  • Hlaváček, David
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number of pages
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  • České vysoké učení technické v Praze. Fakulta strojní
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  • 978-80-01-05484-0
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  • 21220
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